Combustor with resonator

ABSTRACT

A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a combustion chamber, a compressed air passage fluidly coupled to the combustion chamber, and a swirler. At least one acoustic resonator can be provided in the combustor.

CROSS-REFERENCE TO RELATED APPLICATION

This application claims the benefit of U.S. Provisional PatentApplication No. 63/291,539, filed Dec. 20, 2021, which is incorporatedherein by reference in its entirety.

TECHNICAL FIELD

The present subject matter relates generally to a combustor having aresonator, and more specifically to a combustor having a set of acousticresonators for damping.

BACKGROUND

Turbine engines are driven by a flow of combustion gases passing throughthe engine to rotate a multitude of turbine blades. A combustor can beprovided within the turbine engine and is fluidly coupled with a turbineinto which the combusted gases flow.

In a typical turbine engine, air and fuel are supplied to a combustionchamber, mixed, and then ignited to produce hot gas. The hot gas is thenfed to a turbine where it rotates a turbine to generate power.

BRIEF DESCRIPTION OF THE DRAWINGS

In the drawings:

FIG. 1 is a schematic cross-sectional view of a turbine engine having acompressor, a combustor, and a turbine in accordance with variousaspects described herein.

FIG. 2 is a cross-sectional view of the combustor in the turbine engineof FIG. 1 with a swirler in accordance with various aspects describedherein.

FIG. 3 is a cross-sectional view of the swirler of FIG. 2 illustrating aferrule assembly in accordance with various aspects described herein.

FIG. 4 is a cross-sectional view of the swirler of FIG. 2 illustratinganother ferrule assembly in accordance with various aspects describedherein.

DETAILED DESCRIPTION

Aspects of the disclosure described herein are directed to a combustorwith a swirler. For purposes of illustration, the present disclosurewill be described with respect to a turbine engine. It will beunderstood, however, that aspects of the disclosure described herein arenot so limited and that a combustor as described herein can beimplemented in engines, including but not limited to turbojet,turboprop, turboshaft, and turbofan engines. Aspects of the disclosurediscussed herein may have general applicability within non-aircraftengines having a combustor, such as other mobile applications andnon-mobile industrial, commercial, and residential applications.

Turbine engine combustors typically introduce fuel that has beenpremixed with air and then combusted within the combustor to drive theturbine. Increases in efficiency and reduction in emissions have driventhe need to use fuel that burns cleaner or at higher temperatures, suchas utilizing hydrogen fuel. There is a need to improve durability of thecombustor under these operating parameters, including reduction ofselected acoustic dynamics within the combustor such as ringing,vibrational modes, or the like. The inventors' practice has proceeded inthe manner of designing a combustor to meet durability requirements forincreased engine temperatures and the use of hydrogen fuel.

The word “exemplary” is used herein to mean “serving as an example,instance, or illustration.” Any implementation described herein as“exemplary” is not necessarily to be construed as preferred oradvantageous over other implementations. Additionally, unlessspecifically identified otherwise, all embodiments described hereinshould be considered exemplary.

As used herein, the terms “first”, “second”, and “third” may be usedinterchangeably to distinguish one component from another and are notintended to signify location or importance of the individual components.

The terms “forward” and “aft” refer to relative positions within a gasturbine engine or vehicle, and refer to the normal operational attitudeof the gas turbine engine or vehicle. For example, with regard to a gasturbine engine, forward refers to a position closer to an engine inletand aft refers to a position closer to an engine nozzle or exhaust.

As used herein, the term “upstream” refers to a direction that isopposite the fluid flow direction, and the term “downstream” refers to adirection that is in the same direction as the fluid flow. The term“fore” or “forward” means in front of something and “aft” or “rearward”means behind something. For example, when used in terms of fluid flow,fore/forward can mean upstream and aft/rearward can mean downstream.

The term “fluid” may be a gas or a liquid. The term “fluidcommunication” means that a fluid is capable of making the connectionbetween the areas specified.

Additionally, as used herein, the terms “radial” or “radially” refer toa direction away from a common center. For example, in the overallcontext of a turbine engine, radial refers to a direction along a rayextending between a center longitudinal axis of the engine and an outerengine circumference.

All directional references (e.g., radial, axial, proximal, distal,upper, lower, upward, downward, left, right, lateral, front, back, top,bottom, above, below, vertical, horizontal, clockwise, counterclockwise,upstream, downstream, forward, aft, etc.) are only used foridentification purposes to aid the reader's understanding of the presentdisclosure, and do not create limitations, particularly as to theposition, orientation, or use of aspects of the disclosure describedherein. Connection references (e.g., attached, coupled, connected, andjoined) are to be construed broadly and can include intermediatestructural elements between a collection of elements and relativemovement between elements unless otherwise indicated. As such,connection references do not necessarily infer that two elements aredirectly connected and in fixed relation to one another. The exemplarydrawings are for purposes of illustration only and the dimensions,positions, order and relative sizes reflected in the drawings attachedhereto can vary.

The singular forms “a”, “an”, and “the” include plural references unlessthe context clearly dictates otherwise. Furthermore, as used herein, theterm “set” or a “set” of elements can be any number of elements,including only one.

Approximating language, as used herein throughout the specification andclaims, is applied to modify any quantitative representation that couldpermissibly vary without resulting in a change in the basic function towhich it is related. Accordingly, a value modified by a term or terms,such as “about”, “approximately”, “generally”, and “substantially”, arenot to be limited to the precise value specified. In at least someinstances, the approximating language may correspond to the precision ofan instrument for measuring the value, or the precision of the methodsor machines for constructing or manufacturing the components and/orsystems. In at least some instances, the approximating language maycorrespond to the precision of an instrument for measuring the value, orthe precision of the methods or machines for constructing ormanufacturing the components and/or systems. For example, theapproximating language may refer to being within a 1, 2, 4, 5, 10, 15,or 20 percent margin in either individual values, range(s) of valuesand/or endpoints defining range(s) of values. Here and throughout thespecification and claims, range limitations are combined andinterchanged, such ranges are identified and include all the sub-rangescontained therein unless context or language indicates otherwise. Forexample, all ranges disclosed herein are inclusive of the endpoints, andthe endpoints are independently combinable with each other.

FIG. 1 is a schematic view of a turbine engine 10. As a non-limitingexample, the turbine engine 10 can be used within an aircraft. Theturbine engine 10 can include, at least, a compressor section 12, acombustion section 14, and a turbine section 16. A drive shaft 18rotationally couples the compressor section 12 and turbine section 16,such that rotation of one affects the rotation of the other, and definesa rotational axis 20 for the turbine engine 10.

The compressor section 12 can include a low-pressure (LP) compressor 22,and a high-pressure (HP) compressor 24 serially fluidly coupled to oneanother. The turbine section 16 can include an HP turbine 26, and an LPturbine 28 serially fluidly coupled to one another. The drive shaft 18can operatively couple the LP compressor 22, the HP compressor 24, theHP turbine 26 and the LP turbine 28 together. Alternatively, the driveshaft 18 can include an LP drive shaft (not illustrated) and an HP driveshaft (not illustrated). The LP drive shaft can couple the LP compressor22 to the LP turbine 28, and the HP drive shaft can couple the HPcompressor 24 to the HP turbine 26. An LP spool can be defined as thecombination of the LP compressor 22, the LP turbine 28, and the LP driveshaft such that the rotation of the LP turbine 28 can apply a drivingforce to the LP drive shaft, which in turn can rotate the LP compressor22. An HP spool can be defined as the combination of the HP compressor24, the HP turbine 26, and the HP drive shaft such that the rotation ofthe HP turbine 26 can apply a driving force to the HP drive shaft whichin turn can rotate the HP compressor 24.

The compressor section 12 can include a plurality of axially spacedstages. Each stage includes a set of circumferentially-spaced rotatingblades and a set of circumferentially-spaced stationary vanes. Thecompressor blades for a stage of the compressor section 12 can bemounted to a disk, which is mounted to the drive shaft 18. Each set ofblades for a given stage can have its own disk. The vanes of thecompressor section 12 can be mounted to a casing which can extendcircumferentially about the turbine engine 10. It will be appreciatedthat the representation of the compressor section 12 is merely schematicand that there can be any number of blades, vanes and stages. Further,it is contemplated that there can be any number of other componentswithin the compressor section 12.

Similar to the compressor section 12, the turbine section 16 can includea plurality of axially spaced stages, with each stage having a set ofcircumferentially-spaced, rotating blades and a set ofcircumferentially-spaced, stationary vanes. The turbine blades for astage of the turbine section 16 can be mounted to a disk which ismounted to the drive shaft 18. Each set of blades for a given stage canhave its own disk. The vanes of the turbine section can be mounted tothe casing in a circumferential manner. It is noted that there can beany number of blades, vanes and turbine stages as the illustratedturbine section is merely a schematic representation. Further, it iscontemplated, that there can be any other number of components withinthe turbine section 16.

The combustion section 14 can be provided serially between thecompressor section 12 and the turbine section 16. The combustion section14 can be fluidly coupled to at least a portion of the compressorsection 12 and the turbine section 16 such that the combustion section14 at least partially fluidly couples the compressor section 12 to theturbine section 16. As a non-limiting example, the combustion section 14can be fluidly coupled to the HP compressor 24 at an upstream end of thecombustion section 14 and to the HP turbine 26 at a downstream end ofthe combustion section 14.

During operation of the turbine engine 10, ambient or atmospheric air isdrawn into the compressor section 12 via a fan (not illustrated)upstream of the compressor section 12, where the air is compresseddefining a pressurized air. The pressurized air can then flow into thecombustion section 14 where the pressurized air is mixed with fuel andignited, thereby generating combustion gases. Some work is extractedfrom these combustion gases by the HP turbine 26, which drives the HPcompressor 24. The combustion gases are discharged into the LP turbine28, which extracts additional work to drive the LP compressor 22, andthe exhaust gas is ultimately discharged from the turbine engine 10 viaan exhaust section (not illustrated) downstream of the turbine section16. The driving of the LP turbine 28 drives the LP spool to rotate thefan (not illustrated) and the LP compressor 22. The pressurized airflowand the combustion gases can together define a working airflow thatflows through the fan, compressor section 12, combustion section 14, andturbine section 16 of the turbine engine 10.

Turning to FIG. 2 , a generic combustion section 29, suitable for use asthe combustion section 14 of FIG. 1 , is illustrated in further detail.The combustion section 29 can include a combustor 30. The combustor 30can include a combustor inlet 135 fluidly coupled to the compressorsection 12 and a combustor outlet 136 fluidly coupled to the turbinesection 16. The combustion section 29 can include an annular arrangementof fuel injectors 90 each connected to the combustor 30. It should beappreciated that the annular arrangement of fuel injectors 90 can be oneor multiple fuel injectors 90, and that one or more of the fuelinjectors 90 can have different characteristics (e.g. geometricarrangement or profile, or supply different fuel types, or the like). Itwill also be understood that the fuel injector 90 shown is forillustrative purposes only and is not intended to be limiting. Thecombustor 30 can have a can, can-annular, or annular arrangementdepending on the type of engine in which the combustor 30 is located. Ina non-limiting example, an annular arrangement is illustrated anddisposed within a casing 92. The combustor 30 can include an annularcombustor liner 94 and a dome assembly 96 that at least partiallydefines a combustion chamber 98 about a longitudinal axis (LA). Acompressed air passage 110 can be defined at least in part by bothcombustor liner 94 and the casing 92. The compressed air passage 110 canbe fluidly coupled to the combustor inlet 135.

At least one fuel injector 90 can be fluidly coupled to the combustionchamber 98. At least one passage 112 can fluidly connect the compressedair passage 110 and the combustor 30. The at least one passage 112 can,in some examples, be formed by a set of dilution openings 112 a in thecombustor liner 94. Any number of dilution openings can be provided inthe set of dilution openings 112 a. The set of dilution openings 112 acan have any geometric profile, size, pattern, arrangement, or the like,including combinations of varying geometric profiles, sizes, patterns,or arrangements, on or over the combustor liner 94

The fuel injector 90 can be coupled to and disposed within the domeassembly 96 upstream of a flare cone 114 to define a fuel outlet 116.The fuel injector 90 can include a fuel inlet 118 that can be adapted toreceive a flow of fuel (F). The fuel (F) can include any suitable fuel,including hydrocarbon fuel or fuel blend, or hydrogen fuel or fuelblend, in non-limiting examples.

A fuel passage 122 can extend between the fuel inlet 118 and the fueloutlet 116. A swirler 124 can be provided and configured to swirlincoming air in proximity to fuel (F) exiting the fuel injector 90. Insome examples, the swirler 124 can be provided at a dome inlet 120though this need not be the case. The swirler 124 can also be configuredto provide a homogeneous mixture of air and fuel entering the combustor30 in some examples.

The combustor liner 94 can include a liner wall 126 having an outersurface 128 and an inner surface 130 at least partially defining thecombustion chamber 98. In some examples, the liner wall 126 can be madeof one continuous portion, including one continuous monolithic portion.In some examples, the liner wall 126 can include multiple portionsassembled together to define the combustor liner 94. By way ofnon-limiting example, the outer surface 128 can define a first piece ofthe liner wall 126 while the inner surface 130 can define a second pieceof the liner wall 126 that when assembled together form the combustorliner 94. In addition, the combustor liner 94 can have any suitable formincluding, but not limited to, a double-walled liner or a tile liner.

An igniter 132 can be coupled to the liner wall 126 and fluidly coupledto the combustion chamber 98. The igniter 132 can be provided at anysuitable location including, but not limited to, between adjacentdilution openings in the set of dilution openings 112 a.

During operation, compressed air (C) can flow from the compressorsection 12 to the combustor 30 through the compressed air passage 110.At least a portion of the compressed air (C) can pass from thecompressed air passage 110 to the combustion chamber 98 by way of theset of dilution openings 112 a, with the portion defining a dilutionairflow (D).

Some compressed air (C) can be mixed with the fuel (F) and upon enteringthe combustor 30 the mixture is ignited within the combustion chamber 98by one or more igniters 132 to generate combustion gas (G). The dilutionairflow (D) can be supplied through at least the set of dilutionopenings 112 a and mixed into the combustion gas (G) within thecombustion chamber 98, after which the combustion gas (G) can flowthrough combustor outlet 136 and into the turbine section 16.

It should be understood that passages illustrated herein, including thecompressed air passage 110, fuel passage 122, passage 112, and the like,may be shown with components that visually appear to block the passagein the exemplary cross-sectional view shown without actually blockingthe passage. For example, an internal wall, strut, or the like may bepresent in the plane of the exemplary cross-sectional view while thepassage extends into or out of the plane of the exemplarycross-sectional view such that the passage is not actually blocked.

Turning to FIG. 3 , a portion of the combustor 30 is shown proximate thedome assembly 96 and swirler 124. The set of dilution openings 112 a inthe combustor liner 94 is also shown. Compressed air (C) is shown withinthe compressed air passage 110. The fuel (F) is illustrated movingthrough the fuel passage 122 and entering the combustion chamber 98. Itwill be understood that compressed air (C) can also be mixed with fuel(F) within the fuel passage 122 in some examples.

In the illustrated example, the dome assembly 96 can include a deflector140 and a dome plate 142 though this need not be the case. The swirler124 can be positioned upstream of the dome assembly 96 within thecompressed air passage 110. The swirler 124 can include a ferruleassembly 144 at least partially surrounding the fuel passage 122 asshown. The ferrule assembly 144 can include at least one internal fluidpassage 145 having an inlet 146 fluidly coupled to the compressed airpassage 110 and an outlet 148 fluidly coupled to the fuel outlet 116. Inthe non-limiting example shown, the internal fluid passage 145 caninclude a first passage 147 extending through a wall of the ferruleassembly 144, and a plenum 149 at least partially surrounding the fuelpassage 122. The first passage 147 can be fluidly coupled to the inlet146, and the plenum 149 can be fluidly coupled to the outlet 148. Anynumber of internal fluid passages 145 can be provided. The internalfluid passages 145 can have any suitable geometric profile, arrangement,or positioning. In addition, a single internal fluid passage 145 canhave a single inlet 146, multiple inlets 146, a single outlet 148, ormultiple outlets 148. During operation, compressed air (C) can flowthrough the internal fluid passage 145 of the ferrule assembly 144 andenter the combustion chamber 98.

At least one acoustic resonator 150 can be provided with the swirler124. Any number of acoustic resonators 150 can be provided. The acousticresonator 150 can have any suitable form, arrangement, geometricprofile, size, or the like. In some examples, the acoustic resonator 150can include a Helmholtz resonator, a quarter-wave resonator, or ahalf-wave resonator, or the like, or combinations thereof.

In the example of FIG. 3 , the at least one acoustic resonator 150includes a set of quarter-wave resonators 152 coupled to the inlet 146of the internal fluid passage 145 as shown. Any number of acousticresonators 150 can be provided, including only one, or two or more. Inaddition, the set of quarter-wave resonators 152 can include any numberof quarter-wave resonators, including only one, or two or more. In theillustrated example, each quarter-wave resonator of the set ofquarter-wave resonators 152 includes a resonator inlet 154 fluidlycoupled to the compressed air passage 110 and a resonator outlet 156fluidly coupled to the inlet 146 of the internal fluid passage 145. Aresonator chamber 158 can be defined between the resonator inlet 154 andresonator outlet 156. Any suitable geometric profile can be utilized forthe resonator chamber 158, including round, curved, conical, asymmetric,or irregular geometric profiles. In addition, a length of eachquarter-wave resonator of the set of quarter-wave resonators 152 can bedefined between the resonator inlet 154 and resonator outlet 156. Insome examples, a first quarter-wave resonator can have a first lengthand a second quarter-wave resonator can have a second length. The secondlength can be the same as the first length, or smaller than the firstlength, or larger than the first length. It is also contemplated that aninner diameter of a quarter-wave resonator of the set of quarter-waveresonators 152 can be variable, or the set of quarter-wave resonators152 can include a first quarter-wave resonator having a smaller innerdiameter compared to a second quarter-wave resonator, in non-limitingexamples.

The size of the resonator chamber 158 can be selected or designed toattenuate a particular frequency or range of frequencies of acousticwaves, including sound waves or pressure waves, flowing through thecombustor 30. The at least one acoustic resonator 150 can attenuatefrequencies between 2000 Hz and 5000 Hz, or between 4000 Hz and 5000 Hz,in non-limiting examples. In some examples, multiple acoustic resonatorscan be provided wherein a first acoustic resonator can attenuatefrequencies over a first frequency range and a second acoustic resonatorcan attenuate frequencies over a second frequency range. In anon-limiting example, a first acoustic resonator can have a firstchamber volume attenuating frequencies between 2000 Hz and 2500 Hz in afirst portion of the combustor, and a second acoustic resonator can havea second chamber volume attenuating frequencies between 3500 Hz and 4000Hz in a second portion of the combustor. During operation, acousticwaves within the combustor 30 can pass through the ferrule assembly 144and cause resonance within the at least one acoustic resonators 150,thereby damping at least one acoustic frequency and reducing noise,vibrations, or the like.

Referring now to FIG. 4 , another swirler 224 is illustrated that can beutilized with the combustor 30 (FIG. 2 ). The swirler 224 is similar tothe swirler 124; therefore, like parts will be identified with likenumerals increased by 100, with it being understood that the descriptionof like parts of the swirler 124 applies to the swirler 224, exceptwhere noted.

The swirler 224 can be positioned within the combustor 30 upstream ofthe dome assembly 96 within the compressed air passage 110. The swirler224 can include a ferrule assembly 244 similar to the ferrule assembly144 (FIG. 3 ). The ferrule assembly 244 can at least partially surroundthe fuel passage 122 as shown. The ferrule assembly 244 can include aninternal fluid passage 245 having an inlet 246 fluidly coupled to thecompressed air passage 110 and an outlet 248 fluidly coupled to the fueloutlet 116. During operation, compressed air (C) can flow through theinternal fluid passage 245 of the ferrule assembly 244 and enter thecombustion chamber 98.

At least one acoustic resonator 250 can be provided with the swirler224. One difference compared to the acoustic resonator 150 of FIG. 3 isthat the acoustic resonator 250 can include a Helmholtz resonator 252having a resonator inlet 254, a resonator outlet 256, and a resonatorchamber 258. The resonator outlet 256 can be fluidly coupled to theinlet 246 of the internal fluid passage 245. The Helmholtz resonator 252can also include a neck 253 formed by the resonator inlet 254 anddefining a neck volume 255. The resonator chamber 258 can include achamber fluidly coupled to the neck and defining a chamber volume.

Another difference is that the at least one acoustic resonator 250 caninclude a variable chamber volume within the resonator chamber 258. Insome examples, a single resonator chamber 258 can be provided having awall 260 with a thickness that is variable in a circumferentialdirection about the combustor 30. In some examples, multiple internal,circumferentially-arranged dividing walls 261 can be provided to formmultiple circumferentially-arranged acoustic resonators 250 withcorresponding resonator chambers 258. In some examples, a firstresonator chamber 258A can have a first chamber volume 259A and a secondresonator chamber 258B can have a second chamber volume 259B smallerthan the first chamber volume 259A. It should be understood that thefirst resonator chamber 258A extends behind the fuel passage 122 in theillustrated example. In other examples, the resonator chamber 258 caninclude walls with constant thickness, an increasing or decreasingspacing between adjacent walls, a variable geometric profile along apredetermined axis, or the like, or combinations thereof. The set ofacoustic resonators 250 can attenuate frequencies between 1000 Hz and5000 Hz, in some non-limiting examples.

Benefits of the present disclosure include the ability to attenuate oneor more acoustic waves, including pressure waves, high-frequency waves,flow disturbances, or other flow dynamics that may be present within thecombustor. In some examples, multiple frequencies can be attenuatedsimultaneously by selection of chamber volumes formed by the ferruleassembly with integrated acoustic resonators. The use of variablechamber volumes of can additionally provide for selective frequencyattenuation in different regions of the combustor. Attenuation ofundesirable acoustic waves can provide for increased engine efficiencyand increased component part life.

While described with respect to a turbine engine, it should beappreciated that aspects of the disclosure can have generalapplicability to any combustor. Aspects of the disclosure describedherein can also be applicable to engines with propeller sections, fanand booster sections, turbojet engines, or turboshaft engines, innon-limiting examples.

To the extent not already described, the different features andstructures of the various embodiments can be used in combination, or insubstitution with each other as desired. That one feature is notillustrated in all of the embodiments is not meant to be construed thatit cannot be so illustrated, but is done for brevity of description.Thus, the various features of the different embodiments can be mixed andmatched as desired to form new embodiments, whether or not the newembodiments are expressly described. All combinations or permutations offeatures described herein are covered by this disclosure.

Further aspects of the disclosure are provided by the subject matter ofthe following clauses:

A turbine engine, comprising a compressor section, a combustion section,and a turbine section in serial flow arrangement, and the combustionsection having a combustor comprising a combustor liner at leastpartially defining a combustion chamber, a compressed air passagefluidly coupled to the compressor section and the combustion chamber, afuel passage fluidly coupled to the combustion chamber, and a swirler atleast partially surrounding the fuel passage, the swirler comprising aninternal fluid passage having an inlet fluidly coupled to the compressedair passage and an outlet fluidly coupled to the fuel passage, and anacoustic resonator having a resonator chamber fluidly coupled to theinlet of the internal fluid passage.

The turbine engine of any preceding clause, wherein the swirlercomprises a ferrule assembly at least partially surrounding the fuelpassage.

The turbine engine of any preceding clause, further comprising a firstpassage extending through a wall of the ferrule assembly, and alsocomprising a plenum at least partially surrounding the fuel passage.

The turbine engine of any preceding clause, wherein the first passageand the plenum at least partially define the internal fluid passage.

The turbine engine of any preceding clause, wherein the acousticresonator comprises one of a quarter-wave resonator, a half-waveresonator, or a Helmholtz resonator.

The turbine engine of any preceding clause, wherein the acousticresonator comprises a quarter-wave resonator coupled to the inlet of theinternal fluid passage and extending into the compressed air passage.

The turbine engine of any preceding clause, wherein the acousticresonator comprises an outer wall bounding the resonator chamber.

The turbine engine of any preceding clause, wherein the outer wallcomprises a resonator inlet fluidly coupled to the compressed airpassage and a resonator outlet fluidly coupled to the inlet of theinternal fluid passage.

The turbine engine of any preceding clause, wherein the resonatorchamber comprises a first chamber volume, and further comprising asecond resonator chamber having a second chamber volume smaller than thefirst chamber volume.

The turbine engine of any preceding clause, wherein the fuel passage isconfigured to supply hydrogen fuel to the combustion chamber.

A combustor for a turbine engine, comprising a combustor liner at leastpartially defining a combustion chamber, a compressed air passagefluidly coupling a source of compressed air and the combustion chamber,a fuel passage fluidly coupled to the combustion chamber, and a swirlerat least partially surrounding the fuel passage, the swirler comprisingan internal fluid passage having an inlet fluidly coupled to thecompressed air passage and an outlet fluidly coupled to the fuelpassage, and an acoustic resonator having a resonator chamber fluidlycoupled to the inlet of the internal fluid passage.

The combustor of any preceding clause, wherein the swirler comprises aferrule assembly at least partially surrounding the fuel passage.

The combustor of any preceding clause, further comprising a firstpassage extending through a wall of the ferrule assembly, and alsocomprising a plenum at least partially surrounding the fuel passage.

The combustor of any preceding clause, wherein the first passage and theplenum at least partially define the internal fluid passage.

The combustor of any preceding clause, wherein the acoustic resonatorcomprises one of a quarter-wave resonator, a half-wave resonator, or aHelmholtz resonator.

The combustor of any preceding clause, wherein the acoustic resonatorcomprises a quarter-wave resonator coupled to the inlet of the internalfluid passage and extending into the compressed air passage.

The combustor of any preceding clause, wherein the acoustic resonatorcomprises an outer wall bounding the resonator chamber.

The combustor of any preceding clause, wherein the outer wall comprisesa resonator inlet fluidly coupled to the compressed air passage and aresonator outlet fluidly coupled to the inlet of the internal fluidpassage.

The combustor of any preceding clause, wherein the resonator chambercomprises a first chamber volume, and further comprising a secondresonator chamber having a second chamber volume smaller than the firstchamber volume.

The combustor of any preceding clause, wherein the fuel passage isconfigured to supply hydrogen fuel to the combustion chamber.

1. A turbine engine, comprising: a compressor section, a combustion section, and a turbine section in serial flow arrangement, and the combustion section having a combustor comprising: a combustor liner at least partially defining a combustion chamber; a compressed air passage fluidly coupled to the compressor section and the combustion chamber; a fuel passage fluidly coupled to the combustion chamber; and a swirler at least partially surrounding the fuel passage, the swirler comprising: an internal fluid passage having an inlet fluidly coupled to the compressed air passage and an outlet fluidly coupled to the fuel passage; and an acoustic resonator having a resonator chamber fluidly coupled to the inlet of the internal fluid passage.
 2. The turbine engine of claim 1, wherein the swirler comprises a ferrule assembly at least partially surrounding the fuel passage.
 3. The turbine engine of claim 2, further comprising a first passage extending through a wall of the ferrule assembly, and also comprising a plenum at least partially surrounding the fuel passage.
 4. The turbine engine of claim 3, wherein the first passage and the plenum at least partially define the internal fluid passage.
 5. The turbine engine of claim 1, wherein the acoustic resonator comprises one of a quarter-wave resonator, a half-wave resonator, or a Helmholtz resonator.
 6. The turbine engine of claim 1, wherein the acoustic resonator comprises a quarter-wave resonator coupled to the inlet of the internal fluid passage and extending into the compressed air passage.
 7. The turbine engine of claim 1, wherein the acoustic resonator comprises an outer wall bounding the resonator chamber.
 8. The turbine engine of claim 7, wherein the outer wall comprises a resonator inlet fluidly coupled to the compressed air passage and a resonator outlet fluidly coupled to the inlet of the internal fluid passage.
 9. The turbine engine of claim 1, wherein the resonator chamber comprises a first chamber volume, and further comprising a second resonator chamber having a second chamber volume smaller than the first chamber volume.
 10. The turbine engine of claim 1, wherein the fuel passage is configured to supply hydrogen fuel to the combustion chamber.
 11. A combustor for a turbine engine, comprising: a combustor liner at least partially defining a combustion chamber; a compressed air passage fluidly coupling a source of compressed air and the combustion chamber; a fuel passage fluidly coupled to the combustion chamber; and a swirler at least partially surrounding the fuel passage, the swirler comprising: an internal fluid passage having an inlet fluidly coupled to the compressed air passage and an outlet fluidly coupled to the fuel passage; and an acoustic resonator having a resonator chamber fluidly coupled to the inlet of the internal fluid passage.
 12. The combustor of claim 11, wherein the swirler comprises a ferrule assembly at least partially surrounding the fuel passage.
 13. The combustor of claim 12, further comprising a first passage extending through a wall of the ferrule assembly, and also comprising a plenum at least partially surrounding the fuel passage.
 14. The combustor of claim 13, wherein the first passage and the plenum at least partially define the internal fluid passage.
 15. The combustor of claim 11, wherein the acoustic resonator comprises one of a quarter-wave resonator, a half-wave resonator, or a Helmholtz resonator.
 16. The combustor of claim 11, wherein the acoustic resonator comprises a quarter-wave resonator coupled to the inlet of the internal fluid passage and extending into the compressed air passage.
 17. The combustor of claim 11, wherein the acoustic resonator comprises an outer wall bounding the resonator chamber.
 18. The combustor of claim 17, wherein the outer wall comprises a resonator inlet fluidly coupled to the compressed air passage and a resonator outlet fluidly coupled to the inlet of the internal fluid passage.
 19. The combustor of claim 11, wherein the resonator chamber comprises a first chamber volume, and further comprising a second resonator chamber having a second chamber volume smaller than the first chamber volume.
 20. The combustor of claim 19, wherein the fuel passage is configured to supply hydrogen fuel to the combustion chamber. 